CN216232961U - Rotor wing device with strong anti-interference performance and aircraft - Google Patents

Abstract

The utility model discloses a rotor wing device with strong anti-interference performance and an aircraft, comprising a direction changer, a power mechanism and a paddle mechanism, wherein the power mechanism is arranged at the output end of the direction changer and is used for providing rotating force or movably penetrates through the direction changer and is used for transmitting the rotating force; the paddle mechanism comprises a rotating seat, a plurality of paddles and a reinforcing ring, the paddles are evenly arranged on the periphery of the rotating seat along the circumferential direction of the rotating seat, the rotating seat is connected with the output end of the power mechanism, and the inner side of the reinforcing ring is connected with the outer end of each paddle. The rotor wing device can effectively reduce the vibration generated when the blade changes direction at the rotation center, and improve the flying stability; the aircraft is simple in structure and stable in turning flight.

Description

Rotor wing device with strong anti-interference performance and aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to a rotor wing device with strong anti-interference performance and an aircraft.

Background

Unmanned aerial vehicle is generally referred to the aircraft, and present unmanned aerial vehicle mainly divide into two kinds according to the difference of drive lift, and one kind is jet unmanned aerial vehicle, and another kind is rotor type unmanned aerial vehicle. Its size of jet-propelled unmanned aerial vehicle is huge, and flying speed is fast, and the cost is expensive, and the structure is similar with conventional jet-propelled aircraft, and is more in military field.

And rotor type unmanned aerial vehicle, because its drive flight mode with the helicopter is similar, flight speed is slower than jet type unmanned aerial vehicle, simultaneously owing to adopt the mode drive of paddle, for this reason it can realize the structure miniaturization, consequently cites extensively in civilian field. For example, chinese patent CN201520876941.1 discloses an aircraft, which adopts a multi-rotor driving mode and can achieve the adjustment of the flying action and direction of the whole aircraft by controlling the rotation direction and the rotation speed of multiple rotors simultaneously. However, in this aircraft, since the axial direction of each rotor is basically determined relative to the aircraft body, for this reason, when the flight direction needs to be adjusted, the flight state of the aircraft can be changed by requiring different directions of the rotation speed and the rotation direction of a plurality of rotors, and therefore, the flexibility of the aircraft is not high when the direction needs to be adjusted. And the outside one end of rotor in this patent is open, especially when the aircraft diversion or increase and decrease the flight speed of direction of advance, can lead to the axis of rotation direction of rotor to change suddenly relatively ground, and then leads to the outside one end of rotor to take place the atress inhomogeneous suddenly for whole rotor takes place the vibration when keeping normal rotation, and lift is unstable simultaneously. The main reason for the above-mentioned problem is that the rotor is long-strip-shaped, and the rotation center changes in the rotation process, and the plane in which the rotor rotates still keeps the original rotation direction, so that the rotor is easily subjected to flexible deformation after being matched with air in the rotation process, and the lift force is unstable, and the vibration is increased.

Disclosure of Invention

The utility model aims to solve at least one of the technical problems and provides a rotor wing device and an aircraft with strong anti-interference performance, wherein the rotor wing device can effectively reduce the vibration generated when the blade changes direction at the rotation center and improve the flying stability; the aircraft is simple in structure and stable in turning flight.

In order to achieve the purpose, the utility model adopts the technical scheme that:

the rotor wing device with strong interference resistance comprises

A direction changer capable of realizing spatial oscillation and maintaining a changed spatial oscillation angle;

the power mechanism is arranged at the output end of the direction changer and is used for providing rotating force or movably penetrates through the direction changer and is used for transmitting the rotating force;

paddle mechanism, including rotating seat, a plurality of paddle and reinforceing the ring, all the paddle evenly sets up on the periphery of rotating the seat along the circumference direction of rotating the seat, it is connected with power unit's output to rotate the seat, the inboard of reinforceing the ring is connected with the outside one end of paddle.

Furthermore, the two ends of the paddle, the rotating seat and the reinforcing ring are both movable ends, and the inclination lift angle of the paddle can be adjusted.

Further, the direction changer includes

The spherical universal joint is formed by hinging two parts capable of realizing relative spatial swing;

the driving device comprises a main body seat, a first adjusting mechanism and a second adjusting mechanism, wherein the main body seat is arranged on any one part, the first adjusting mechanism and the second adjusting mechanism are respectively arranged on any one part, the output ends of the first adjusting mechanism and the second adjusting mechanism are respectively connected with the other part, and the first adjusting mechanism and the second adjusting mechanism can simultaneously or respectively and independently drive the two parts to spatially swing around a hinge point;

wherein, power unit installs and is used for providing the turning force or activity wears to establish in the ball universal joint and is used for transmitting the turning force on the main part seat.

Further, the first adjusting mechanism comprises a first rack and a first driving assembly, two ends of the first rack are respectively hinged to two opposite sides of the part which is not provided with the main body seat, the first driving assembly is arranged on the main body seat, and an output end of the first driving assembly can be always meshed with the first rack; the second adjustment mechanism comprises a second rack and a second driving assembly, wherein the second rack and the second driving assembly are provided with two sets, of the second rack are symmetrically arranged on two sides of the first rack, two sets are arranged at one end of the second rack and are respectively arranged on the main body seat, the other end of the second rack is a movable end, and the second driving assembly can be respectively rotatably arranged on the non-arranged side wall of the main body seat and is two sets.

Furthermore, the power mechanism is a driving motor, the driving motor is installed on the main body seat, and the rotating seat is connected with the output end of the driving motor.

Furthermore, the power mechanism is a three-section type universal joint, the three-section type universal joint is movably arranged in the spherical universal joint in a penetrating mode, two ends of the three-section type universal joint respectively penetrate through the two parts in a rotating mode, one end, close to the main body seat, of the three-section type universal joint movably penetrates through the main body seat, and two ends of the three-section type universal joint can adjust the transmission direction along with the swinging of the two parts on the spherical universal joint; and the rotating seat is connected with the output end of the three-section type universal joint.

Furthermore, the two groups of second driving assemblies respectively comprise a rotating frame, a servo motor and a gear arranged on the output end of the servo motor, the two groups of rotating frames can be rotatably arranged on two side walls of the part which is not provided with the main body seat, the servo motor is arranged on the rotating frames, the two second racks can be respectively inserted into the rotating frames on the corresponding side and meshed with the gear in the rotating frames on the corresponding side, and the second racks can drive the rotating frames to rotate relative to the part which is not provided with the main body seat through the matching of the gears.

Further, two the part is unable adjustment base and spherical seat respectively, spherical seat is the hemisphere structure at least, the appearance chamber has in the unable adjustment base, install in the opening that holds the chamber spherical seat shutoff, spherical seat can carry out the space swing around holding the chamber, main part seat is installed on spherical seat, and first adjustment mechanism and second adjustment mechanism are all installed on unable adjustment base or spherical seat, first adjustment mechanism and second adjustment mechanism's output is connected with spherical seat or unable adjustment base respectively, first adjustment mechanism and second adjustment mechanism all can drive spherical seat relative unable adjustment base space swing simultaneously or separately.

Furthermore, the spherical seat comprises a bowl-shaped cover and a magnetic ring assembly, one side of an opening of the bowl-shaped cover is buckled in an opening of the containing cavity, and the bowl-shaped cover can rotate around the center of the sphere relative to the opening of the containing cavity and always block the opening of the containing cavity; the magnetic ring assembly is arranged in the cavity and is used for adsorbing the bowl-shaped cover on the opening of the cavity all the time.

Aircraft, including aircraft body and interference immunity strong rotor device.

The utility model has the beneficial effects that:

the rotor wing device can realize spatial swing and keep a changed spatial swing angle by utilizing the direction changer, is beneficial to installing the power mechanism, is convenient to change the rotation direction of the paddle mechanism, and finally achieves the effect of changing the flight state. The structure of the direction changer enables the power output direction of the whole power mechanism to be stable and adjustable, and the direction changer is suitable for various application occasions and convenient to control in the later period. In addition, connect through reinforceing the ring at the outside one end of paddle, can effectively improve the intensity of the outside one end of paddle for when paddle mechanism changes at the rotation center direction, reinforceing the ring and can reducing the anti deformability who makes the outside one end of paddle, improve the rotational stability of whole paddle mechanism, reduce the vibration. The aircraft has simple structure, and effectively keeps stable flight state when the rotor wing device turns.

Drawings

The following detailed description of embodiments of the utility model is provided in conjunction with the appended drawings, in which:

fig. 1 is a first schematic structural diagram according to a first embodiment of the present invention;

FIG. 2 is a second schematic structural diagram according to a first embodiment of the present invention;

FIG. 3 is a schematic structural diagram according to a second embodiment of the present invention;

FIG. 4 is a schematic structural view of a paddle mechanism in an embodiment of the utility model;

FIG. 5 is a first schematic structural diagram of a direction changer in an embodiment of the present invention;

FIG. 6 is a second schematic structural diagram of a direction changer in an embodiment of the present invention;

FIG. 7 is a cross-sectional view of a diverter in an embodiment of the present invention.

In the figure: the power mechanism 100, the driving motor 110, the three-section type universal joint 120, the paddle mechanism 200, the rotating base 210, the paddle 220, the reinforcing ring 230, the ball universal joint 300, the fixed base 310, the accommodating cavity 311, the mounting hole 312, the vertical portion 313, the closing portion 314, the base bottom 315, the main body block 316, the limiting ring base 317, the ball base 320, the bowl-shaped cover 321, the inner magnetic ring 322, the outer magnetic ring 323, the main body base 410, the first adjusting mechanism 420, the first rack 421, the first driving assembly 422, the second adjusting mechanism 430, the second rack 431, the second driving assembly 432, the rotating frame 4321 and the gear 4322

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When a component is referred to as being "connected" to another component, it can be directly connected to the other component or intervening components may also be present. When a component is referred to as being "disposed on" another component, it can be directly on the other component or there can be intervening components, and when a component is referred to as being "disposed in the middle," it is not just disposed in the middle, so long as it is not disposed at both ends, but rather is within the scope of the middle. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.

Referring to fig. 1-7, the present application provides an aircraft including an aircraft body and a high interference immunity rotor arrangement. The rotor wing device with strong anti-interference performance comprises a direction changer, a power mechanism 100 and a blade mechanism 200, wherein the direction changer can realize spatial swing and keep a changed spatial swing angle; the paddle mechanism 200 comprises a rotating base 210, a plurality of paddles 220 and a reinforcing ring 230, wherein all the paddles 220 are uniformly arranged on the periphery of the rotating base 210 along the circumferential direction of the rotating base 210, the rotating base 210 is connected with the output end of the power mechanism 100, and the inner side of the reinforcing ring 230 is connected with the outward end of the paddle 220. The power mechanism 100 is installed at the output end of the direction changer and is used for providing a rotating force or movably penetrates through the direction changer and is used for transmitting the rotating force; wherein the deviator is mounted on the aircraft body for providing a steering function.

It should be added to note that, the aircraft in this application can be the integrated unmanned aerial vehicle after the rotor is got rid of for the conventionality, for example patent 201510396487.4-many rotor unmanned aerial vehicle aircraft system that has the fire control reconnaissance function, and the deviator in this application can be installed on the horn on the above-mentioned unmanned aerial vehicle aircraft, can also reduce the quantity of horn simultaneously on the prerequisite that does not change the performance, can also realize the diversion of whole unmanned aerial vehicle aircraft like this. In the application, the unmanned aerial vehicle is driven by electric power and oil power, if electric driving is adopted, the power mechanism 100 is directly installed on the output end of the direction changer, and the power mechanism 100 is directly connected with the blade mechanism 200; if oil power is used for rotation, the power mechanism 100 needs to pass through the direction changer and provide a rotational force to the paddle mechanism 200. In addition, the redirector may be a conventional multi-link redirecting structure, such as a conventional multi-link spindle structure found on a vehicle tire.

Referring further to fig. 1 to 4, the rotor device of the present invention can implement spatial oscillation and maintain a changed spatial tilt angle by using the direction changer, which is beneficial to installing the power mechanism 100, facilitating to change the rotation direction of the blade mechanism 200, and finally achieving the effect of changing the flight state. The structure of the direction changer enables the power output direction of the whole power mechanism 100 to be stable and adjustable, and the direction changer is suitable for various application occasions and convenient for later control. In addition, connect through reinforceing ring 230 at the outside one end of paddle 220, can effectively improve the intensity of the outside one end of paddle 220 for when paddle mechanism 200 changes at the rotation center direction, reinforceing ring 230 can reduce the anti deformability who makes the outside one end of paddle 220, improves the rotational stability of whole paddle mechanism 200, reduces the vibration. The aircraft has simple structure, and effectively keeps stable flight state when the rotor wing device turns.

Referring to fig. 4, in the present application, in order to achieve different lift effects, both ends of the blade 220, to which the rotating base 210 and the stiffening ring 230 are connected, are movable ends, and the tilt angle of the blade 220 can be adjusted. The structure for adjusting the pitch angle of the blades 220 can be implemented as described in patent 201410428211.5, which is incorporated in a rotorcraft rotor comprising a primary pitch horn and a secondary horn, and is not described in detail herein. Further, in the present application, four or more sets of blades 220 are provided, which can enhance the strength of the entire blade mechanism 200.

With further reference to fig. 1, 2, 3, 5, 6 and 7, in order to provide a direction changer with simple structure and convenient direction control and locking, the direction changer comprises a ball joint 300 and a driving device 400, wherein the ball joint 300 is formed by hinging two components capable of realizing relative spatial swinging; the driving device 400 comprises a main body seat 410, a first adjusting mechanism 420 and a second adjusting mechanism 430, wherein the main body seat 410 is installed on any one of the components, the first adjusting mechanism 420 and the second adjusting mechanism 430 are respectively installed on any one of the components, output ends of the first adjusting mechanism 420 and the second adjusting mechanism 430 are respectively connected with the other component, and the first adjusting mechanism 420 and the second adjusting mechanism 430 can simultaneously or respectively and independently drive the two components to spatially swing around a hinge point; the power mechanism 100 is installed on the main body mount 410 and is used for providing a rotational force or movably inserted into the ball joint 300 and transmitting the rotational force.

In practice, the ball joint 300 may be a conventional ball and socket joint configuration. In actual use, the two components can be locked relative to each other, so as to maintain the space angle of the external structure on the main body seat 410 or on the component not mounted on the main body seat 410. The driving device 400 may have another structure in the present application, for example, a structure in which a driving wheel directly drives a movable member of the ball joint 300 to operate, or a structure in which a plurality of telescopic links are extended and contracted, and the opposite swinging of two members of the ball joint 300 is controlled by a plurality of sets of telescopic links in different directions. Of course, other embodiments are not limited to the above-listed embodiments. In fact, the first adjustment mechanism 420 and the second adjustment mechanism 430 may be a common telescopic arm structure, or may be rotatably mounted on any one of the components by using a roller, the roller abuts against the spherical outer wall of the other component, and the roller is used to directly drive the abutted component to swing relative to the other component. In practice, the installation angles of the first adjustment mechanism 420 and the second adjustment mechanism 430 cannot be coplanar, and the directions in which the first adjustment mechanism 420 and the second adjustment mechanism 430 drive the two components to swing are not coplanar, and in practical installation, it is preferable that the first adjustment mechanism 420 and the second adjustment mechanism 430 are both installed on the same installation surface of the fixed component, and the two adjustment mechanisms are vertically distributed on the installation plane.

Further, this application provides a specific structure of ball-and-socket joint 300, two the part is unable adjustment base 310 and spherical seat 320 respectively, spherical seat 320 is the hemisphere structure at least, it has chamber 311 in unable adjustment base 310, install in the opening that holds chamber 311 with spherical seat 320 shutoff, spherical seat 320 can carry out the space oscillation around holding chamber 311, main part seat 410 is installed on spherical seat 320, and first adjustment mechanism 420 and second adjustment mechanism 430 are all installed on unable adjustment base 310 or spherical seat 320, the output of first adjustment mechanism 420 and second adjustment mechanism 430 is connected with spherical seat 320 or unable adjustment base 310 respectively, first adjustment mechanism 420 and second adjustment mechanism 430 all can drive spherical seat 320 relatively unable adjustment base 310 space oscillation simultaneously or separately. In fact, the inner wall of the cavity 311 abuts against the outer surface of the spherical end of the spherical seat 320, which ensures the tightness of the connection. In fact, the open end of the cavity 311 is provided with a limiting structure to prevent the spherical seat 320 from falling out of the cavity 311. In fact, the first adjusting mechanism 420 and the second adjusting mechanism 430, the main body seat 310 is installed on the spherical seat 320, the first adjusting mechanism 420 and the second adjusting mechanism 430 can be installed on the fixed base 310 or the spherical seat 320, if the installation ends of the first adjusting mechanism 420 and the second adjusting mechanism 430 are installed on the fixed base 310, the action ends of the first adjusting mechanism 420 and the second adjusting mechanism 430 are connected with or hinged or abutted to the spherical seat 320; similarly, the mounting ends of the first adjusting mechanism 420 and the second adjusting mechanism 430 are both mounted on the spherical seat 320, and the action ends of the first adjusting mechanism 420 and the second adjusting mechanism 430 are both connected with, hinged to, or abutted against the fixed base 310. The specific installation configuration of the first adjusting mechanism 420 and the second adjusting mechanism 430 is only required to be able to drive the fixed base 310 and the spherical seat 320 to swing around the hinge point space simultaneously or separately.

In some embodiments, in order to make the spherical seat 320 simpler and have a certain controllability, the spherical seat 320 includes a bowl-shaped cover 321 and a magnetic ring assembly, an opening side of the bowl-shaped cover 321 is buckled in the opening of the cavity 311, and the bowl-shaped cover 321 can rotate around its spherical center in space relative to the opening of the cavity 311 and always close off the opening of the cavity 311; the magnetic ring assembly is installed in the cavity 311 and is used for adsorbing the bowl-shaped cover 321 on the opening of the cavity 311 all the time. In practical use, the position of the bowl-shaped cover 321 in the cavity 311 is not fixed, that is, the position of the center of the bowl-shaped cover 321 in the cavity 311 is not fixed, so that the mobility of the whole ball joint 300 can be increased. The magnetic ring subassembly main role is in this application for the motion of spacing bowl shape cover 321, and in fact, holds the chamber 311 opening part and is provided with position sensing, can detect the displacement of bowl shape cover 321, can also control the adsorption affinity of magnetic ring subassembly according to bowl shape cover 321 apart from holding the open-ended position of chamber 311 simultaneously, increases whole ball-and-socket joint 300's use flexibility like this.

Referring to fig. 7, in a modified embodiment, the magnetic ring assembly comprises an inner magnetic ring 322 and an outer magnetic ring 323, the outer magnetic ring 323 is installed on the inner wall of the cavity 311, and the inner ring abuts against the outer wall of the bowl-shaped cover 321; the inner magnet ring 322 is mounted on the inner wall of the bowl-shaped cover 321 in the opening area, and the inner magnet ring 322 and the outer magnet ring 323 can attract each other. Wherein, the inner magnetic ring 322 and the outer magnetic ring 323 are both provided with rollers, which is convenient for the bowl-shaped cover 321 to swing. In fact, in some embodiments, driving members are disposed inside the inner magnetic ring 322 and the outer magnetic ring 323, and the driving members can be connected to the rollers, that is, the rollers can realize the directional swing of the bowl-shaped cover 321. Generally speaking, rollers may be disposed at four equal positions of the inner magnetic ring 322 and the outer magnetic ring 323, and two adjacent rollers or a plurality of rollers in a desired adjustment direction are used to drive the bowl-shaped cover 321 to move, so as to achieve the swing adjustment of the bowl-shaped cover 321.

Indeed, in some embodiments, in addition to using a position sensor to detect the position of the bowl-shaped cover 321 within the cavity 311, the cavity 311 may be modified such that the bowl-shaped cover 321 is able to move within the cavity 311. The receiving cavity 311 comprises a vertical portion 313 and a closing-in portion 314, the diameter of the vertical portion 313 is larger than or equal to that of the bowl-shaped cover 321, the diameter of the opening end of the closing-in portion 314 is smaller than that of the bowl-shaped cover 321, and the bowl-shaped cover 321 can slide along the vertical portion 313. In fact, the cavity 311 may be a separate structure to achieve the installation of the bowl-shaped cover 321, and in some embodiments, the fixing base 310 may also be a separate structure to achieve the installation of the bowl-shaped cover 321 into the cavity 311.

With further reference to fig. 1 to 7, the fixing base 310 includes a base 315 and a main body block 316 mounted on the base 315, the cavity 311 is disposed in the main body block 316, and the opening is disposed on a side away from the base 315. The base 315 is a plate-shaped structure, and the base 315 is provided with a plurality of mounting holes 312, which facilitates the mounting work in the later period. Of course, the body block 316 may be a hemisphere or a square block, and the cross section of the cavity 311 is a circle, so as to fit the hemisphere of the bowl-shaped cover 321.

In fact, referring to fig. 6, in one embodiment of the present application, in order to prevent the bowl-shaped cover 321 from coming out of the cavity 311, the fixed base 310 further comprises a limit ring seat 317, the limit ring seat 317 is mounted on one side of the body block 316 at the opening of the cavity 311, the outer surface of the spherical seat 320 abuts against the inner wall of the inner ring of the limit ring seat 317, and the limit ring seat 317 can limit the spherical seat 320 in the cavity 311. Wherein, the limiting ring seat 317 can be fixed on the main body block 316 through screws, which facilitates later disassembly. In fact, in some embodiments, the limiting ring seat 317 has a rubber pad on its inner wall, and the rubber pad has a lubricant on it, so as to reduce the wear on the outer spherical surface of the spherical seat 320.

With further reference to fig. 1 to 7, in order to better achieve the oscillation of the spherical seat 320 with respect to the fixed base 310; in one embodiment of the present application, the first adjusting mechanism 420 includes a first rack 421 and a first driving assembly 422, two ends of the first rack 421 are respectively hinged to two opposite sides of the component which is not provided with the main body seat 410, the first driving assembly 422 is provided on the main body seat 410, and an output end of the first driving assembly 422 can always keep engaged with the first rack 421; the second adjusting mechanism 430 includes a second rack 431 and a second driving assembly 432, the second rack 431 and the second driving assembly 432 are both provided with two sets, two the second rack 431 is symmetrically arranged on two sides of the first rack 421, two one ends of the second rack 431 are respectively arranged on the main body base 410, the other ends are movable ends, the second driving assembly 432 is respectively rotatably arranged on the side wall of the component of the main body base 410, and the second driving assembly 432 is respectively engaged with the second rack 431 corresponding to one side all the time and can swing along with the second rack 431. In fact, the main body seat 310 is installed on the spherical seat 320, and two ends of the two first racks 421 are respectively hinged on the outer wall of the fixed base 310. The fixed base 310 is mounted on an external fixed structure in the present embodiment, and the spherical seat 320 is a movable end, on which a load structure, such as a driving structure in the field of unmanned aerial vehicles, an actuating end on a multi-axis mechanical arm, an actuating end on a precision instrument, etc., can be mounted on the main body seat 310.

It should be noted that, two sets of in this application second drive assembly 432 all includes and rotates frame 4321, servo motor and install the gear 4322 on the servo motor output, and is two sets of rotate frame 4321 and can install respectively non-rotatably the main part seat 410 on the both sides wall of part, servo motor installs on rotating frame 4321, two second rack 431 all can the cartridge respectively in the rotation frame 4321 that corresponds one side, and with correspond the gear 4322 meshing in the frame 4321 of one side rotation, second rack 431 can drive through gear 4322's cooperation and rotate the frame 4321 and install relatively non-the part of main part seat 410 rotates. In practice, two sets of the rotating frames 4321 are rotatably mounted on the fixed base 310, respectively, while the fixed base 310 is provided with rotating posts on both sides, on which the corresponding rotating frames 4321 are rotatably mounted. In addition, in order to facilitate the cooperative rotation, the second rack 431 is an outer rack, and the gear 4322 presses against the second rack 431, so that the gear 4322, the servo motor and the rotating frame 4321 can follow the spatial angular variation of the second rack 431 when the second rack 431 swings following the space of the spherical seat 320 due to the deformation of the second rack 431.

Referring further to fig. 3 to 7, in order to better drive the rotating base 210 to rotate based on the above-mentioned direction changer structure, in one embodiment, the power mechanism 100 is a driving motor 110, the driving motor 110 is mounted on the main body base 410, and the rotating base 210 is connected to an output end of the driving motor 110. In the embodiment, since the power mechanism 100 directly drives the paddle mechanism 200 to rotate, the direction changer is actually only used as a direction changing structure for changing direction in the electrically driven aircraft, so that the stability and the flexibility of direction change of the aircraft in the flying process can be improved. In practice, the main body seat 410 is provided with a plurality of mounting holes for mounting and fixing the driving motor 110.

Referring further to fig. 1, 2, 4 to 7, in practical use, in this embodiment, the driving motor 110 is used to directly drive the paddle mechanism 200 to rotate, when the rotation center of the paddle mechanism 200 is inclined, the vibration transmitted by the paddle mechanism 200 directly acts on the driving motor 110, which is easy to cause damage, and increases the use cost in the later period, and meanwhile, the endurance of the electrically driven aircraft is limited, which restricts the use environment of the whole aircraft. Therefore, another specific embodiment of the power mechanism 100 is provided in another embodiment of the present application, wherein the power mechanism 100 is a three-section type universal joint 120, the three-section type universal joint 120 is movably inserted into the ball-and-socket joint 300, and two ends of the three-section type universal joint 120 respectively penetrate through two parts in a rotatable manner, one end of the three-section type universal joint 120 close to the main body seat 410 movably penetrates through the main body seat 410, and two ends of the three-section type universal joint 120 can adjust a transmission direction along with the swinging of the two parts on the ball-and-socket joint 300; the rotating base 210 is connected to an output end of the three-segment type universal joint 120. In this embodiment, the aircraft body is powered by fuel, and for this purpose the three-piece joint 120 has its input connected to the output of a fuel engine on the aircraft body to provide power. In addition, in this embodiment, since the end of the three-segment type universal joint 120 connected to the rotating base 210 is a movable end, the fixed base 310 and the ball base 320 of the ball-and-socket type universal joint 300 are respectively a fixed end and a movable end, and respectively fix and limit the input end and the output end of the three-segment type universal joint 120, which acts to lock the transmission direction of the three-segment type universal joint 120. In addition, the fuel engine and the paddle mechanism 200 on the aircraft body are connected through the three-section type universal joint 120, the structure formed by the three-section type universal joint 120 and the direction changer can also play a role in buffering vibration, particularly the paddle mechanism 200 transmits the radial transmission to the three-section type universal joint 120, the vibration of the whole aircraft body is reduced, and the flying quality is improved.

The above embodiments are only for illustrating the technical solutions of the present invention and are not limited thereto, and any modification or equivalent replacement without departing from the spirit and scope of the present invention should be covered within the technical solutions of the present invention.

Claims (10)

1. The rotor wing device with strong interference resistance is characterized by comprising

A direction changer capable of realizing spatial oscillation and maintaining a changed spatial oscillation angle;

the power mechanism is arranged at the output end of the direction changer and is used for providing rotating force or movably penetrates through the direction changer and is used for transmitting the rotating force;

paddle mechanism, including rotating seat, a plurality of paddle and reinforceing the ring, all the paddle evenly sets up on the periphery of rotating the seat along the circumference direction of rotating the seat, it is connected with power unit's output to rotate the seat, the inboard of reinforceing the ring is connected with the outside one end of paddle.

2. The rotor device with high interference resistance of claim 1, wherein two ends of the blade, which are connected with the rotating seat and the reinforcing ring, are movable ends, and the tilt lift angle of the blade can be adjusted.

3. A high interference immunity rotor apparatus as recited in claim 1, wherein said direction changer includes

The spherical universal joint is formed by hinging two parts capable of realizing relative spatial swing;

the driving device comprises a main body seat, a first adjusting mechanism and a second adjusting mechanism, wherein the main body seat is arranged on any one part, the first adjusting mechanism and the second adjusting mechanism are respectively arranged on any one part, the output ends of the first adjusting mechanism and the second adjusting mechanism are respectively connected with the other part, and the first adjusting mechanism and the second adjusting mechanism can simultaneously or respectively and independently drive the two parts to spatially swing around a hinge point;

wherein, power unit installs and is used for providing the turning force or activity wears to establish in the ball universal joint and is used for transmitting the turning force on the main part seat.

4. The high interference immunity rotor apparatus of claim 3, wherein the first adjusting mechanism comprises a first rack and a first driving assembly, two ends of the first rack are respectively hinged on two opposite sides of the component which is not provided with the main body seat, the first driving assembly is arranged on the main body seat, and an output end of the first driving assembly can always keep meshed with the first rack; the second adjustment mechanism comprises a second rack and a second driving assembly, wherein the second rack and the second driving assembly are provided with two sets, of the second rack are symmetrically arranged on two sides of the first rack, two sets are arranged at one end of the second rack and are respectively arranged on the main body seat, the other end of the second rack is a movable end, and the second driving assembly can be respectively rotatably arranged on the non-arranged side wall of the main body seat and is two sets.

5. The rotor wing device with high interference resistance of claim 3 or 4, wherein the power mechanism is a driving motor, the driving motor is mounted on the main body seat, and the rotating seat is connected with the output end of the driving motor.

6. The rotor wing device with strong interference resistance according to claim 4, wherein the power mechanism is a three-section type universal joint, the three-section type universal joint is movably arranged in the ball-shaped universal joint in a penetrating manner, two ends of the three-section type universal joint respectively penetrate through the two parts in a rotatable manner, one end of the three-section type universal joint close to the main body seat movably penetrates through the main body seat, and two ends of the three-section type universal joint can adjust the transmission direction along with the swinging of the two parts on the ball-shaped universal joint; and the rotating seat is connected with the output end of the three-section type universal joint.

7. The rotor wing device with high interference immunity according to claim 4, wherein two sets of the second driving assemblies each include a rotating frame, a servo motor and a gear installed on an output end of the servo motor, the two sets of the rotating frames are rotatably installed on two side walls of the component which is not installed with the main body seat, respectively, the servo motor is installed on the rotating frames, two second racks can be respectively inserted into the rotating frames on the corresponding side and engaged with the gear in the rotating frames on the corresponding side, and the second racks can drive the rotating frames to rotate relative to the component which is not installed with the main body seat through cooperation of the gears.

8. The rotor device with the strong interference immunity according to claim 3, wherein the two components are a fixed base and a spherical seat respectively, the spherical seat is at least of a hemispherical structure, the fixed base has a cavity therein, the spherical seat is installed in an opening of the cavity in a sealing manner, the spherical seat can swing spatially around the cavity, the main body seat is installed on the spherical seat, the first adjusting mechanism and the second adjusting mechanism are both installed on the fixed base or the spherical seat, output ends of the first adjusting mechanism and the second adjusting mechanism are connected with the spherical seat or the fixed base respectively, and the first adjusting mechanism and the second adjusting mechanism can drive the spherical seat to swing spatially relative to the fixed base simultaneously or independently.

9. The rotor wing device with high interference resistance according to claim 8, wherein the spherical seat comprises a bowl-shaped cover and a magnetic ring assembly, one side of the opening of the bowl-shaped cover is buckled in the opening of the cavity, the bowl-shaped cover can rotate around the sphere center of the bowl-shaped cover in space relative to the opening of the cavity and can always block the opening of the cavity; the magnetic ring assembly is arranged in the cavity and is used for adsorbing the bowl-shaped cover on the opening of the cavity all the time.

10. Aircraft, comprising an aircraft body, characterized in that it further comprises a tamper-resistant rotor arrangement according to any of claims 1-9.

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